# TCDS E-129: Pratt & Whitney Division

- Type: Type certificate data sheet
- Status: Current
- Holder: Pratt & Whitney Division
- Revision: 8
- Revised: February 1, 1974
- Product: Engine
- Data sheet PDF: https://openairdocs.org/files/sha256/ca/bf/cabf5483c64c790886a7109058ba2dd9d2426ad017219471d663d0c2243fa669
- FAA DRS: https://drs.faa.gov/browse/excelExternalWindow/BDACA434D72D69928525670D005F7090.0001
- Page: https://openairdocs.org/tcds/E-129

## Models (6)

As the data sheet lists them.

- Wasp S1H1
- Wasp R-1340-61
- Wasp S1H4
- Wasp S3H2
- Wasp S1H1-G
- Wasp S1H2

## What the data sheet says

From the PDF's text layer, line by line; tables lose their columns. The PDF is the record.

```text
Page No. 1 2
Rev No. 8 8
Reformatted 11/93.
FEDERAL AVIATION ADMINISTRATION
E-129
Revision 8
Pratt & Whitney
Wasp S1H1
S1H1-G
S1H2
S1H4
S1H5-G (See Note 11)
S3H2
R-1340-61
February 1, 1974
AIRCRAFT ENGINE SPECIFICATION No. E-129
Engines of models described herein conforming with this specification and approved data on file with the Federal Aviation
Administration meet the minimum standards for use in certificated aircraft in accordance with pertinent aircraft specifications and
applicable portions of the Civil Air Regulations provided they are installed, operated, and maintained as prescribed by the approved
manufacturer's manuals and other approved instructions.
Manufacturer Pratt & Whitney Aircraft
Division of United Aircraft Corporation
East Hartford, Connecticut
Model Wasp S1H1, S1H2 S1H4 S1H1-G R-1340-61 S3H2
Type   9RA Direct drive - - 3.2 reduction gearing - - Direct drive
Rating (Impeller gear ratio) 12:1 - - - - - - 10:1
  Maximum continuous
    hp, rpm, in.Hg., at:
      Critical altitude (ft.) 550-2200-33.0-8000 - - - - - - 550-2200-32.5-5000
      Sea level, pressure altitude 550-2200-35.0-S.L. - - - - - - 550-2200-34.0-S.L.
  Takeoff (five minutes),
    hp, rpm, in.Hg. 660-2250-36.5 - - - - - - 600-2250-36.0
(See NOTE 10)
Fuel (Minimum grade av. gas) 80/87 - - - - - - - -
Lubricating oils See P&WA - - - - - - - -
Service Bulletin No. 1183
Bore and stroke, in. 5.75 X 5.75 - - - - - - - -
Displacement, cu. in. 1344 - - - - - - - -
Compression ratio 6:1 - - - - - - - -
Weight (dry), lbs. 865, 868 879 930 950 878
Propeller shaft, SAE No. 40 - - - - - - - -
Carburetion Stromberg NA-Y9E1 carburetor - - - - - - - -
Ignition, dual Scintilla SB9-RN-4 magnetos - - - - - - Scintilla SB9R
Ignition timing, °BTC 25 - - - - - - - -
Spark plugs See P&WA Service Bulletin No. 1175 - - - - - - - -
NOTES 1, 2, 3, 4, 5, 6, 7, 10 1, 2, 3, 5, 7 1, 2, 3, 4, 6, 10 1, 2, 3, 6 1, 2, 3, 5, 7
"- -" indicates "same as preceding model."
"__" indicates "does not apply."
NOTE 1.  Maximum permissible temperatures are as follows:
Cylinder Head (Well type thermocouple) Cylinder Barrel Oil Inlet
500°F 335°F 200°F

E-129 Page 2
NOTE 2:  Fuel and oil pressure limits:
Fuel pressure (psi) 3-6 Oil pressure (psi) 70-90
Except R-1340-61, 3-5
NOTE 3.  The following accessory drives are provided:
Direction of Speed Ratio Maximum Torque
Rotation (Clockwise (Times crank- (in.-lb.) **Maximum overhang
or Counter-clockwise) shaft speed) Continuous  Static (in.-lb.)
Starter CC 1.0 2300 10000 180
Generator  C 1.5 100 300 183
Generator (opt)  C 2.0 140 500 183
(Except R-1340-61)
Fuel Pump CC 1.0 150 450 10
Aux. Accessory CC 1.0 *150 450 10
Tachometer  R.H.  C .5 15 45 10
                   L.H. CC
Governor  C 1.144 60 250 - -
Vacuum Pump  C 1.5 *100 300 10
*Maximum combined drive load of Vacuum Pump must not exceed 150 in. lb.
**Maximum allowable accessory moments in inch pounds, provided no destructive accessory drive
or mounting pad forces resulting from accessory vibration are present.
Early Wasp Engines incorporate tongue and groove fuel and vacuum pump drives.  All later engines
have spline type drives.
NOTE 4. Eligible with an automatic power and mixture control with the NA-Y9C carburetor at a weight
increase of 12 lbs.
NOTE 5. Incorporates both 9th and 4-1/2 order dynamic dampers.
NOTE 6. Eligible with rear crankcase section fabricated from aluminum alloy instead of magnesium alloy
at a weight increase of 13 lbs.
NOTE 7. The S1H2, S3H2 and S1H4 engines are approved for helicopter application and operation.  The
S1H2 and S3H2 differ principally from the S1H1 in having a modified lubrication system and a new
carburetor adapter.  These modifictions were made in order to enable these engines to operate
properly when mounted at an upward angle of 45° from the horizontal position.  The S1H4 engine
is the same as the S1H2 engine except that it incorporates the oil scavenging provisions of the
R-1340-55 engine and a carburetor elbow to permit operation in a vertical attitude.  R-1340-61 is
the same as S1H1-G except for dry weight.
NOTE 8. Deleted April 16, 1959.
NOTE 9. Deleted February 1, 1974.
NOTE 10. (a)  Ratings are based upon the best power mixture strength and 400°F cylinder head temperature.
(b)  A takeoff manifold pressure at 38.0" Hg. may be used with grade 91/96 fuel for S1H1 and
     S1H1-G engines.
NOTE 11. The approval for Models S1H2-G and S1H5-G has expired.  None of these engines were
manufactured.
--  END  --
```

## ADs (3, in force first)

- [AD 99-11-02](https://openairdocs.org/ad/99-11-02): Cylinders Inspections · Pratt & Whitney Division Military R-1340 Series, Wasp R-1340-59, Wasp R-1340-61 and 7 more. Effective Jul 19, 1999
- [AD 96-15-02](https://openairdocs.org/ad/96-15-02): Crankshaft counterweight · Pratt & Whitney Division Military R-1340 Series, Wasp S1H1, Wasp S1H1-G and 2 more. Effective Aug 12, 1996
- [AD 56-06-02](https://openairdocs.org/ad/56-06-02): Cylinder Flange Attaching Stud · Pratt & Whitney Division Double Wasp CA15, Double Wasp CA17, Double Wasp CA18 and 115 more

## STCs approved under this data sheet (16)

- [STC SE04651CH](https://openairdocs.org/stc/SE04651CH): To allow use of l00R grade aviation fuel meeting Swift Fuel, LLC specification SPEC-l00R-22. Swift Fuels LLC
- [STC SE01966WI](https://openairdocs.org/stc/SE01966WI): Use of GAMI G100UL High Octane Unleaded Avgas in spark ignition piston aircraft engines. General Aviation Modifications Inc.
- [STC SE5189NM](https://openairdocs.org/stc/SE5189NM): Installation of chip detector light system.. A & L Aircraft Parts Inc
- [STC SA4005NM](https://openairdocs.org/stc/SA4005NM): Precise Flight Inc. Pulselite Control System. Precise Flight Inc
- [STC SE01200LA](https://openairdocs.org/stc/SE01200LA): Installation of Pratt & Whitney R-2800 engine cylinder assemblies on altered P&WA R-1340 engine models. Aircraft Cylinder & Turbine Inc.
- [STC SE09538SC](https://openairdocs.org/stc/SE09538SC): Installation of American Bosch magneto and ignition harness, model SB9RU-3 magneto and P/N 165373 harness, or SB9RC-3 magneto and PN 165374 harness.. Covington Aircraft Engines, Inc.
- [STC SE09477SC](https://openairdocs.org/stc/SE09477SC): Installation of a propeller nose oil seal.. A & L Aircraft Parts, Inc
- [STC SE919NE](https://openairdocs.org/stc/SE919NE): Replacement of P&W P/N C-13670(Gear-floating blower drive) with Windsor Aerospace P/N WA-C-13670 and P&W P/N 11768 (Cam) with Windsor Aerospace P/N WA-11768.. Windsor Gear and Drive Inc
- [STC SE09029SC](https://openairdocs.org/stc/SE09029SC): Install chip detector system on P&W R-1240 series engines.. Air Tractor, Inc
- [STC SE00274NY](https://openairdocs.org/stc/SE00274NY): Installation of a Windsor Gear and Drive replacement crankshaft, P/N WA-270458.. Windsor Gear and Drive Inc
- [STC SE6069NM](https://openairdocs.org/stc/SE6069NM): Removal of inverted flight check valve from Stromberg NA-R9B and NA-Y9E1 series carburetors.. Aero Engines Inc.
- [STC SE2658NM](https://openairdocs.org/stc/SE2658NM): Replacement of type design P&W P/N 11768 engine with Precision Aero-Parts, Inc. P/N R-1768. Precision Aero-Parts Inc.
- [STC SE5584SW](https://openairdocs.org/stc/SE5584SW): Propeller shaft oil seal.. Page Industries, Inc
- [STC SE1864CE](https://openairdocs.org/stc/SE1864CE): Operation of engine on unleaded automotive gasoline.. Petersen Aviation Inc
- [STC SE41N](https://openairdocs.org/stc/SE41N): Increase in compression ratio to 6.75:1, substitution of 12:1 impeller ratio and other modifications to R-1340 engines, equivalent to S1H2, S3H1 and S3H2(not equipped with reduction gear).. CRMA6, Rue Marceau
- [STC SE741SW](https://openairdocs.org/stc/SE741SW): R-1830 rockershaft assemblies.. Southwest Airmotive Co

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